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From ATV to ATV Evolution

From ATV to ATV Evolution. Transportation for In-Orbit Infrastructure and beyond. February 2004 Hans-Jörg Heidmann. DEBRIS AVOIDANCE BY ISS. ISS REFUELING. ISS ORBIT CONTROL. WATER AND GAS. ISS ATTITUDE CONTROL. GYRODYNES/CMG DESATURATION. Major features of ATV mission. DRY CARGO.

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From ATV to ATV Evolution

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  1. From ATV to ATV Evolution Transportation for In-Orbit Infrastructure and beyond February 2004 Hans-Jörg Heidmann Presentation title – file name – date

  2. DEBRIS AVOIDANCE BY ISS ISS REFUELING ISS ORBIT CONTROL WATER AND GAS ISS ATTITUDE CONTROL GYRODYNES/CMG DESATURATION Major features of ATV mission DRY CARGO RETRIEVAL OF WASTE AND DESTRUCTION DURING REENTRY Presentation title – file name – date

  3. General layout and characteristics • Mass = 20.5 tons at launch • dry mass : 11 tons • gross cargo : 9.5 tons • up to 8 tons of propellant at launch • Sizes • 10.3 m length • 4.5 m diameter • 22.3 m with deployed solar wings (4.8 kW) • 22 m3 pressurized module (16 m3 for pressurized cargo) Presentation title – file name – date

  4. ATV subsystems • Power supply :- 4 independent distribution chains with rotative solar panels (Si) and rechargeable batteries (NiCd) • Data Management System :- 3 Failure Tolerant Computers running the main Flight Applicative Software • Monitoring and Safety Chain : - 2 independent and autonomous chains for Rendezvous monitoring and Collision Avoidance Maneuver with specific means (data processor, category A software, primary power sources, thrusters…) • Propulsion Subsystem :- 28 ACS thruster (240N) - 4 OCS thrusters (490 N)- 8 propellant tanks (8 tons of MON + MMH) • Semi passive TCS : - 40 Variable Conductance Heat Pipes Presentation title – file name – date

  5. ATV subsystems (cont’d) • External Rendezvous monitoring by the ISS : - Visual Video Target - RF Kurs navigation transponder - Visual Ranging Cues • Navigation and Monitoring of RV :- Relative GPS - Laser sensors (2 Telegoniometer + 2 Videometers) • General navigation equipment : - Star Tracker, Accelerometer, Gyrometer, Sun Sensor for survival • Communicationsubsystem :- 2 chains compatible TDRSS/Artemis for ATV-CC - 2 chains (S-band) for proximity link with ISS Presentation title – file name – date

  6. ATV subsystems (cont’d) • Pressurized Module :- 22 m3 pressurized module - up to 8 Standard Racks - Environment and Control Life Support (fan, smoke detector, light) • Unpressurized Cargo Tanks : - 3 water tanks - 3 Gas tanks - 2 refueling kits • Russian Docking System :- Active Docking Unit featuring mechanical, fluidic, electrical and data interface • Russian Equipment Control Set :- 2 redundant equipment chains to control interfaces with ISS Presentation title – file name – date

  7. ESA EADS-ST (F+D) ALENIA SPAZIO (I) CONTRAVES SPACE (CH) DUTCH SPACE (NL) EADS SODERN (F) DJO (D) ATV INDUSTRIAL TEAM ATV Flight Segment Prime Contractorship. System engineering. Verification of ATV FS. Development of Flight Software. Development and Procurement of Propulsion and Reboost subsystem and of Avionics Chains. ATV assembly, integration and testing. Support to ESA for external interfaces. Cargo Carrier development and integration. Russian equipment set procurement Thermal control studies. Development of Spacecraft structure subsystem. Development of Solar Generation subsystem. Development of Videometer and Star Tracker. Development of Telegoniometer Presentation title – file name – date

  8. 1st ATV flight model at overall integration EquippedPropulsion Bay IntegratedCargo Carrier EquippedAvionics Bay Launcher adapterwith separation system 1st ATV launch by Ariane 5(Jules-Verne)scheduled May 2005 ATV sub-assembliesdelivered at EADS-ST Bremen - Nov. 2003 Presentation title – file name – date

  9. Servicing of the US-Segment • The NASA Shuttle fleet will be retired from up to 2010, which could lead to a logistical gap for the ISS at least until 2014 • This logistical gap could be overcome by ATV derived unmanned transportation vehicles such as: - ATV Download System - Cargo Capsule System - Unpressurized Logistic Carrier • For the logistic supply of the US-Segment by ATV could be developed a special docking mechanism called IBDM (International Docking and Berthing Mechanism). Presentation title – file name – date

  10. 2. Scenario Description (6) PTV Scenario • Lift-off • Separation of Ariane 5 EAPs • Fairing jettisoning • Separation of the EPC • Ignition of the ESP • Separation of the ESP • Separation completed • PTV attitude stabilized • Solar panels deployed • Antennas deployed • Check-up by the PTV control centre • Transfer to the phasing orbit • Maneuver 1 • Drift period 1 • Maneuver 2 • Phasing • Drift period 2 • Mid course correction • Drift period 3 • Transfer to the ISS vicinity – • Interface with the RV scenario Presentation title – file name – date

  11. 2. Scenario Description (7) PTV Scenario -V-bar Approach Scenario Presentation title – file name – date

  12. 2. Scenario Description (8)ISS Attached and Return Phase • Checkout prior to reentry • Transfer of the state vector and reentry • information to GNC of reentry vehicle • Deorbit impulse • Separation of the ATV Propulsion part • Separation of the docking adapter • Reentry • Hypersonic flare • Descent • Back cover jettison • Parachute sequence deployment • (for instance, extractor, drogue chute, main chute) • Heat shield jettison • Landing • Landing system deployment (airbag) • Touch down • Vehicle passivation and safing • Beacon and post-landing systems deployment • Arrival of ground crew • Manual vehicle safing • Hatch opening and express payload removal • Hoisting on transport vehicle • Transport • Connections • Repressurization of inter volume and tightness control • Hatch opening • PTV power down to stand by mode • Payload operations • PTV power up out of stand by mode • Check out • Hatch closing • Depressurization of inter volume • Unlatch • Separation • Distancing • Orbit correction • Drift • Reentry vehicle power-up (avionics / GNC) • Wetting of propulsion system of the reentry vehicle (pyro valve) • Pyros armed • Checkout prior to reentry • Transfer of the state vector and reentry information to GNC of reentry vehicle • Deorbit impulse • Separation of the ATV Propulsion part • Separation of the docking adapter Presentation title – file name – date

  13. 2. Scenario Description (9)CTV scenario • Mission Scenario similar • To PTV • Safeguard Scenario during • Launch phase • Two-Failure Tolerance • Required • ATV S/C Modification • Analysis led to the Result • that it would be the design • of a new Vehicle Presentation title – file name – date

  14. 2. Scenario Description (10) ULC Mission Scenario • Launch by Ariane 5 ECA • After nominal separation from AR5 upper stage jettisoning of ULC cover/cargo door • ULC operates in a safe orbit below ISS orbit • ULC conducts ISS approach similar to the ATV after ISS okay • Final Approach differs from ATV due to different docking locations • ULC approach is similar with PTV • ULC will be docked at Node 2 Port • Exchange of complete platform pallets or of single ORUs by SSRMS and/or Special Purpose Dexterous System • Pallets attachment places are at the truss (starboard, port) via PAS, UCCAS or ULCAS • De-docking Leaving approach ellipsoid • Braking manoeuvres for initiating of de-orbiting Presentation title – file name – date

  15. 4. PTV System Architect. & ATV S/CModifications (2) Capsule adaptor module upper I/F close to capsule intermediate diameter, Front docking module Same configuration for CTV but with Additional redundancies • CoG of capsule close to I/F plane Capsule adapter module • CoG of complete vehicle below I/F plane • I/F on a 20° cone structure  No separation interference • I/F as far as possible from nose (Reentry thermal aspect) Presentation title – file name – date

  16. 4. PTV System Architect. & ATV S/CModifications (3) Presentation title – file name – date

  17. 4. CTV System Architect. & ATV S/CModifications (1) Global architecture choice (1) Vehicle launch with Ariane5 ESC-B (23.0 tons capacity) US-port (V-bar as baseline, -R-bar as back-up treated by delta compared to V-bar) IBDM device Same reentry capsule as PTV configuration Autonomous reentry capsule (no power, thermal regulation, … deliveries) No refuel, no reboost No emergency detachment requirements 1 month docking phase • Capsule adaptor module slightly modified compared to PTV • Same Front Docking module • Emergency Escape module added • Modified Ariane5 fairing added Presentation title – file name – date

  18. 4. CTV System Architect. & ATV S/CModifications (5) CTV Crew & P/L Accommodation Results (Crew of 5) • Blunt Biconic shape launched “nose-down”, 4.4 m ext. diameter, 5 crew member • PC internal volume of 25.8 m³ • PC equipment volume 9.1 m³ (preliminary figure) • Considering 2 m³ per crew member of free volume, 6.7 m³ can be occupied by payload. • Considering: • 20% volume margin to account for secondary structures and packaging factors • payload density of about 300 Kg per cubic meter the theoretical P/L occupying all the residual volume of about 6.7m³ is 1600 Kg • Considering a Capsule mass of 13.1 tons: • The mass w/o P/L is 10.32 tons • Potential P/L Mass is 2.78 tons • Also assuming a tilting of 30 deg for seats in landing configuration the biconic shape can easily accommodate a crew of 5 Presentation title – file name – date

  19. 6. ULC System Architect. & ATV S/CModifications (1) ATV-ULC Layout and Configuration • Unpressurized cargo bay • Doors jettisoned before circularization • Cargo on 2 Express pallets (Boeing) or ICC pallets (EADS-ST) • Front cone with stan- dard RV equipment and Common Berthing Mech- anism (CBM) • SSRMS grapple on aft bay wall Presentation title – file name – date

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